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某民用大涵道比涡扇发动机风扇缩尺试验件气动性能数值仿真

朱芳 陈云永 卫飞飞 金东海 王延荣 桂幸民

朱芳, 陈云永, 卫飞飞, 金东海, 王延荣, 桂幸民. 某民用大涵道比涡扇发动机风扇缩尺试验件气动性能数值仿真[J]. 航空动力学报, 2013, 28(7): 1539-1548.
引用本文: 朱芳, 陈云永, 卫飞飞, 金东海, 王延荣, 桂幸民. 某民用大涵道比涡扇发动机风扇缩尺试验件气动性能数值仿真[J]. 航空动力学报, 2013, 28(7): 1539-1548.
ZHU Fang, CHEN Yun-yong, WEI Fei-fei, JIN Dong-hai, WANG Yan-rong, GUI Xing-min. Numerical simulation of aerodynamic performance of scaled fan of a civil high-bypass-ratio turbofan engine[J]. Journal of Aerospace Power, 2013, 28(7): 1539-1548.
Citation: ZHU Fang, CHEN Yun-yong, WEI Fei-fei, JIN Dong-hai, WANG Yan-rong, GUI Xing-min. Numerical simulation of aerodynamic performance of scaled fan of a civil high-bypass-ratio turbofan engine[J]. Journal of Aerospace Power, 2013, 28(7): 1539-1548.

某民用大涵道比涡扇发动机风扇缩尺试验件气动性能数值仿真

基金项目: 国家自然科学基金(50736007,51006005,51236001)

Numerical simulation of aerodynamic performance of scaled fan of a civil high-bypass-ratio turbofan engine

  • 摘要: 根据某民用航空发动机大涵道比风扇1/2缩尺试验任务的需求,利用三维数值模拟软件对该风扇缩尺试验件各个转速下的内、外涵气动性能进行了数值仿真分析,并对缩尺几何、弹性恢复角及涵道比等参数对风扇缩尺试验件内、外涵气动性能的影响进行了对比分析.结果表明:该风扇缩尺试验件各转速下的内、外涵性能都基本达到设计指标;几何缩尺分别引起了风扇外涵、内涵设计点的效率分别降低了1.26%,0.77%;80%转速下,叶尖弹性恢复角减小0.36°使风扇外涵稳定工作裕度扩展了4.04%,但近设计点总压比和效率均有所衰减;双涵道风扇在不同涵道比状态下,内、外涵相互影响,流量-总压比及流量-绝热效率特性是在一定范围内的曲线带.

     

  • [1] 黄家骅,冯国泰.航空发动机特性仿真技术的进展与展望[J].推进技术,2002,23(4):346-351. HUANG Jiahua,FENG Guotai.Development and expectation of performance simulation in aviation engine[J].Journal of Propulsion Technology,2002,23(4):346-351.(in Chinese)
    [2] Dawes W N.The simulation of three-dimensional viscous flow in turbomachinery geometries using a solution-adap- tive unstructure mesh methodology [R].ASME paper 1991-GT-124,1991.
    [3] Denton J D.An improved time marching method for turbomachinery flow calculation[J].Journal of Engineering for Gas Turbines and Power,1983,105(7):514-521.
    [4] Denton J D.The calculation of fully three dimensional flow through any type of turbomachine blade row[R].AGARD LS 140,1985.
    [5] Hah C.Calculation of three-dimensional viscous flow in turbornachinery with an implicit relaxation method[J].Journal of Propulsion and Power,1987,3(5):415-422.
    [6] Hah C,Loellbach J.Development of hub corner stall and its influence on the performance of axial compressor blade rows[J].ASME Journal of Turbomachinery,1999,121(1):66-67.
    [7] Adamczyk J J.Model equation for simulation flows in multistage turbine [R].ASME Paper 1985-GT-152,1985.
    [8] Roberto B,Emesto B.Shock/boundary-layer/tip-clearance interaction in a transonic rotor blade[J].Journal of Propulsion and Power,2009,25(3):668-677.
    [9] 宁方飞.考虑真实几何复杂性的跨声压气机内部流动的数值模拟 [D].北京:北京航空航天大学,2002. NING Fangfei.Numerical investigations of flows in tran-sonic compressors with real geometrical complexities [D].Beijing:Beijing University of Aeronautics and Astronau-tics,2002.(in Chinese)
    [10] 李泯江.单转子叶尖间隙多块网格的跨声压气机数值模拟及设计研究 [D].北京:北京航空航天大学,2004. LI Minjiang.Numerical investigations and design of tran-sonic compressor with tip clearance flow using multi-block mesh [D].Beijing:Beijing University of Aeronautics and Astronautics,2004.(in Chinese)
    [11] 尹松,金东海,朱芳,等.湍流模型对压气机数值模拟精度的影响[J].航空动力学报,2010,25(12):2683-2689. YIN Song,JIN Donghai,ZHU Fang,et al.Influence of turbulence models on simulation of a compressor[J].Journal of Aerospace Power,2010,25(12):2683-2689.(in Chinese)
    [12] 李晓娟,桂幸民.风扇/增压级设计与非设计性能数值模拟术[J].推进技术,2005,26(6):522-525. LI Xiaojuan,GUI Xingmin.Numerical simulation of fan/compressor design and off-design performance[J].Journal of Propulsion Technology.2005,26(6):522-525.(in Chinese)
    [13] 桂幸民,李晓娟.基于低雷诺数条件的风扇/增压级气动设计[J].燃气涡轮试验与研究,2007,20(3):18-22. GUI Xingmin,LI Xiaojuan.Aerodynamic design of fan/compressor operated at low Reynolds number [J].Gas-Turbine Experiment and Research,2007,20(3):18-22.(in Chinese)
    [14] 冀国锋.轴流/离心压气机通用叶片造型设计系统及应用. [D].北京:北京航空航天大学,2009. JI Guofeng.A general blading design system and its application for axial/centrifugal compressor [D].Beijing:Beijing University of Aeronautics and Astronautics,2009.(in Chinese).
    [15] 金东海,桂幸民.某涡扇发动机多级高负荷风扇/压气机气动性能数值模拟[J].航空动力学报,2011,26(5):1059-1065. JIN Donghai,GUI Xingmin.Numerical simulation of highly loaded multi-stage fan/compressor of a turbofan engine[J].Journal of Aerospace Power,2011,26(5):1059-1065.(in Chinese)
    [16] 陈葆实.大涵道比风扇和增压级气动设计难点分析 [R].广东 深圳:大型飞机关键技术高层论坛暨中国航空学会2007年学术年会,2007.
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出版历程
  • 收稿日期:  2013-03-19
  • 刊出日期:  2013-07-28

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